Brake for airplanes



Feb. 9 1926.

' H. E. BAUGHMAN BRAKE FOR AIRPLANES' 1925 2 Sheets-Sheet 1 Filed Nov. 14

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Feb. 9 1926. 1,572,834

H. E. BAUGHMAN BRAKE FOR AIRPLANES Filed NOV. 14 1925 2 Sheets-Sheet 2 Patented Feb. 9, 1926.

UNITED STATES PATENT OFFICE.

HAROLD E. BALUGHMAN, OF WA'IQERLOO, IOWA.

BRAKE FOR AIRPLANES.

Application filed Novtinber 14, 1925. SeriaI'No. 69,043.

To all whom it may concern:

Be it known'that I, HAROLD E. BAUG-H MAN, a citizen of the United States, residing at Waterloo, in the county of Black Hawk and State of Iowa, have invented certain new and a useful Improvements in Brakes for Airplanes, of which the following is a specification.

This invention relates to brakes for airplanes and has for one of its objects to pro vide a device of this character which will shown in Fig. 1;

be simple in construction, comparatively inexpensive to manufacture and install, and more eflicient in use than those which have been heretofore proposed.

A further object of provide an airplane brake which is comparatively light in weight and so compact that when closed or in the inoperatlve pos1-. tion, it will not create an excessive amount of air resistance.

With the above and other objects inview,

which will appear as the description proceeds, the invention consists in the novel details of construction and combinations and arrangements of parts, more fully herein after described and particularly pointed out in the appended claims.

, Referring to the accompanying drawmgs, forming a part of this specification, in which like reference characters designate like parts in all the views;

Fig. 1 is a front elevational view of a conventional form of biplane, showing a brake constructed in accordance with the'present invention, in operative position thereon; Fig. 2 is a top plan view of the pa Fig. 3 is a side elevational view of the parts shown in Fig. 1, as seen from the right of the said figure;

Fig. 4, is an enlarged horizontal sectional plan View showing one of the braking mechanism in detail; and,

Fig. 5 is an enlarged fragmentary eleva- Ytional view of a portion of the parts shown in Fi 4, as viewed from the plane indicated %y the line 5-5 of the sa d figure.

.Referring more particularly to the said drawings, the numeral 10 indicatesgenerally,-an airplane of the well. known biplane type provided with the usual fuselage 11, landing gear 12, upper wing 13, lower wing 14, and propeller 15, driven by any suitable source of 'power not shown. The braking mechanism constituting the present inventhe invention is to 1 tion comprises two, units, which in the biplane type of machine are mounted between the upper and lower wings13 and 14, one

on either side of the fuselage 11. Sinceor hollowed out as at 17 to accommodate the forward edges of the brake wings, to be more fully described below, when the latter are in their inoperative positions to the end that the air resistance of the brake, when in this position will be reduced to a minimum. 1

The brake proper, comprises a pair of substantlally rectangular aerofoils or brake wings 18'and 19, which are vertically mount- .ed between the upper an'd'lower wings 13 and 14 of the plane. The upper edges of the said aerofoils are provided with the pinsor projections 20 and 21, slidably mounted in suitable guides 22, which are secured in any desired manner, beneath the upper wing 13. The said guides as willbe best understood from Figs. 2 and 4, are arranged in pairs, one to either side of the master strut 16 and comprise rearwardly extending straight portions 23 which converge slightly toward the rear, and forward curved portions 24 which extend at substantially right angles to either side of the said Strut 16. I

. The lower edges of the aerofoils 18 and 19 are provided with similar pins ,or projections which are slidably mounted in complementary guides or tracks 25 which are suitably secured to the lower wing 14 of the machine.

.In order that the aerofoils 18 and 19 may be moved from their rearward folded or inoperative position to the forward operative position, shown in full lines in Flg. 4, I.

provide the links 26, one of the ends of which is pivotallyconnected to the pin v20 of each aerofoil, while the other ends of the said links are pivotally connected as at 27,

to the sliding blocks 28 and 29, slidably to hold them in such ositions as the force mounted upon a suitable guide member or of the mud itself, wil accomplish this re-.

rod 30. These blocks 28'and 29 are'secured sult. v

While the invention has been illustrated as wil and described, as applied to an air lane of now be explaine v p the biplane type, 1t may obvious y, with The cable 31 is an endless one which slight modifications, .be accommodated to passes around a pulley or drum 32 rigidly mono lanes and triplanes. carried by a vertically journalled shaft 33 f re, oapparent that thoseiskllled in the arranged in the forward end of the fuselage art may vary the detalls, of construction as to a cable 31 which serves to simultaneousl move. them in (apposite directions,

It will, there- 11, as will b lear from Fig 1, 2 and 3, well as the precise arrangements of parts Th id bl extends along beneath the without departing from the s irit of the inforward edge of thflupliler wing .13, to an vention and, it is .not wishe to be limited idler pulley 34 about w ich it passes and t0 the above disclosure except as may be rethen returns to the drum 32. The sliding qlllr d by the clalms.

block 28 is secured in an suitable manner What 1s claimed is:

to the rear run of the cab e, while the block 1- loan airplane, a strut member, the rear 29 is likewise secured to the forward run of 13011110118 0f Wi are i f y aerofoils the said cable so that upon any movement IIOI'IIlRlly POSltlOIlGd behlnd Silld strut memof the cable in' either direction, the said her 111 P I1 S s bstantiall parallel to the blocks will be moved in opposite directions, P3 of W ndtr v lwlth t elr forward poras will be readily understood from Fig. 4. lqns ln' h w y 1 1 1 115 of sold strut, Th t f th bl k ill, f sad aerofolls bemg movable therefrom to course, through the rin s 26, produce corre- Positions at the Sides of Said Strut a sponding movements 0 the aerofoils 18and s a fll g e t said path of travel; and 19,'co'nnected thereto, so that they will be means f r movlng sald aer0f01ls.' moved from operative to inoperative posibrake f r alrc raft comprlslng aerotions, and vice versa, according to the movef011$ a ap e to n rm lly occupy positions ments f th bl 31, a v substantlall parallel to the path of wind A similar cable 35 is similarly attached vel; gm es di p ed above and be ow nd to the lower portion of the aerofoils 18 and e g h Pfl h of movement of Said aero- 19, through corresponding blocks and links Q P J QDS carried by said aerofoils and passes around a drum 36, carried-by the Slldably engagln sald. guldes; and means lower end of the shaft 33. The said shaft r m vlng Sal aerofolls in'said guides 33 also carries intermediate the drums 32 whereby they may be caused to occupy osiand 36, another drum or pulle 37 around tions at substantlal angles to said pat of which passes an operating cab e 38, which v extends backward in the fuselage, to the 3. brake for aircraft comprising a cockpit 39, where it is provided wlth suitplurallty of aerofoils; guides for said aeroable terminals 40, by means of which it may foils having straight and curved ortions, be manually operated by the aviator to ac-' said straight portions being adapte to) distuate the braking aerofoils 18 and 19 as pose said aerofoils substantiall parallel to above described. the path of wind travel, and sai curved por It will thus be seen-that this invention tIOIIS serving to dispose, Said aerofoils at provides a sim 1e and effective brake for substantial angles to said ath of travel; airplanes, whic may be easily controlled and'means for movin sai aerofoils from by the aviator from the cockpit or from the 16 p tion Of d gul s to he other. s1de of the fuselage of the machine, to the 4. A brake for aircraft comprising 9. end that the speed of the plane may .be pair of substantially vertical aerofoils; quickly checked when desired, thus facilitatguides for said aerofoils having straight and ing landing in small fields and on rou h or curved portions, -said straight portions bebog y ground, and the landing of seapiane's ing adapted todispose said aerofoils subon t 1e decks of ships since the s eed of the stantiall parallel to'the path of wind travel, plane may be. guickly checked efore and and sai curved portions serving to dispose during the lan ing process. Furthermore said aerofoils at substantial angles to said the nose of the plane will not tip or dive path oftraveland means for simultaneous, nor will the machine chan e its iorizontai 1y moving said aerofoils in said guides from position during landin i equipped with oneposition to the other. this brake. It will also e noted that owing 5. A brake for aircraft comprising a pair to the peculiar arrangement of the parts, of substantially vertical aerofoils; 11 per when the aerofoils are in their operative poand lower pairs of guides for said aero 011s, sitions, they occupy planes at an angle to having substantiall parallel straight porthe direction of the wind against them, from tions and opposite y disposed curved porwhich it results that when once'set in these tions, said straight ortions bein adapted positions, 1t 1s not necessary for the aviator to dispose said aero oils substantially parallel to the path" of wind travel, and said curved portions serving to dispose said aerofoils at substantial angles to said path of w travel; and means for simultaneously mov- 5 'ing said aerofoils in said guides from one 1 foils, having substantially (parallelstraight portions and oppositely isposed curved portions, said straight portions being adapted to dispose said aerofoils substantially parallel to the path of wind travel, and said curved portions serving to dispose said aerofoils at substantial angles to said ath of travel; an endless cable; connections etween said aerofoils and opposite runs of said cable; and means for moving said cable.

A brake for aircraft comprising a pair 2 a of substantially vertical aerofoils; upper and lower pairs of guides for said aerofoils, having substantially parallel straight portions-a'nd oppositely disposed curved por-.-'

tions, said straight portions bein adapted allel' to the path of wind travel, and said curved portions serving to dispose said aerofoils at substantial angles to said path of travel; an endless cable; a guiderod; a pair of blocks slidably mounted on said guide rod, each of which is connected to.an opposite run of said cable; links connecting said blocks and aerofoils; and-means for moving said cable.

In testimony whereof I afiix my signature; r 4

HAROLD E. BAUGHMAN.

25 Q to dispose said aerofoils' substantlally .par- 

